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N1 SYNC ON 18−10−40
N2 SYNC ON 18−10−41
EPR CMD SYNC ON 18−10−41
N1, N2, EPR CMD SYNC OFF 18−10−42
SYNC Annunciation 18−10−42
Thrust Reverser System 18−10−43
Thrust Reverser 18−10−44
Reverse Thrust Operation 18−10−45
Reverser Components 18−10−46
Isolation Control Unit 18−10−46
Directional Control Unit 18−10−46
Reverse Thrust Levers 18−10−48
Reverser System LockOut
18−10−49
Starting and Ignition 18−10−50
Starter Air Valve (SAV) 18−10−52
Air Turbine Starter (ATS) 18−10−52
Ignition System 18−10−53
Engine Run Switches 18−10−54
Engine Starting 18−10−56
Engine Shut Down 18−10−61
Dry Cranking 18−10−62
Wet Cranking 18−10−62
Starting Anomalies 18−10−63
AutoRelight
18−10−64
Quick Relight 18−10−64
POWER PLANT
TABLE OF CONTENTS
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
18−00−2
Page
DESCRIPTION
Engine Fire Detection System 18−10−65
Engine Limit Exceedance Display 18−10−66
Power Plant EICAS Messages 18−10−67
EMS CIRCUIT PROTECTION
CB − Engine System 18−20−1
CB − Oil System 18−20−2
CB − Thrust Rev System 18−20−4
POWER PLANT
TABLE OF CONTENTS
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
18−00−3
Page
POWER PLANT
TABLE OF CONTENTS
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
18−00−4
THIS PAGE INTENTIONALLY LEFT BLANK
GENERAL
The Global Express airplane is powered by two BMW−Rolls Royce BR 700−710A2−20 engines,
each mounted on a pylon on either side of the rear fuselage.
The engine is an axial flow, dual shaft turbofan, with a 4.2:1 bypass ratio, rated at 14,750 lbs of thrust
at sea level at ISA.
The BR 700−710A2−20 engine contains two main rotating assemblies (spools), a single stage low
pressure (LP) fan driven by a two stage turbine and a ten stage high pressure (HP) compressor,
driven by a two stage turbine. The HP spool provides an external drive for the accessories mounted
on the accessory gearbox.
The engine is made up of eight modules as follows:
· Fan assembly.
· Fan case.
· Intermediate case.
· HP Compressor.
· HP Turbine and combustion chamber.
· LP Turbine and shaft.
· Accessory Gearbox (AGB).
· Bypass duct.
Each engine provides bleed air extraction, from either the 5th stage or the 8th stage of compression,
for Air Conditioning and Pressurization, Cowl and Wing antiicing
and/or engine starts.
The engine oil system consists of a lubrication system, a heat management system and an oil
replenishment system.
The fuel system consists of a low pressure system and a high pressure system. Fuel is supplied from
the airplane fuel system via AC and/or DC fuel pumps and engine driven fuel pumps.
Thrust management is controlled throughout all phases of operation by the Full Authority Digital
Electronic Control (FADEC). An Electronic Engine Controller (EEC) is the major part of the FADEC,
interfacing between the airplane and the engine.
Primary engine indications are displayed on EICAS and secondary indications on the STATUS page.
Autothrottle is controlled by the autothrottle computer, located in the IAC and sends signals to
FADEC via the throttle, for thrust commands.
Starting is initiated through the FADEC, to provide normal ground/air starts, alternate ground/air
starts, wet and dry motoring and continuous ignition. Starting can also be performed manually.
The thrust reverser system is operated by the airplane hydraulic system and is controlled by the
EEC.
Vibration monitoring system provides signals indicating N1 (Fan) and N2 (HP compressor) vibration
levels on each engine.
Fire detection is provided by dual element sensor assemblies connected in series to provide two
independent sensing loops. Two fire bottles are located at the rear of the airplane.
POWER PLANT
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
18−10−1
ENGINE ASSEMBLY AND AIRFLOW
The BR 700−710A2−20 engine contains two main rotating assemblies (spools), a single stage low
　
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